US9145216B2 - Unified chemical electric propulsion system - Google Patents

Unified chemical electric propulsion system Download PDF

Info

Publication number
US9145216B2
US9145216B2 US13/223,041 US201113223041A US9145216B2 US 9145216 B2 US9145216 B2 US 9145216B2 US 201113223041 A US201113223041 A US 201113223041A US 9145216 B2 US9145216 B2 US 9145216B2
Authority
US
United States
Prior art keywords
propellant
thruster
supply arrangement
chemical
accelerator
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US13/223,041
Other versions
US20130047578A1 (en
Inventor
Nicolas Claude Gascon
Mark Antony Cappelli
Ronald W. King
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SPACE SYSTEMS/LORAL A DELAWARE LLC LLC
Maxar Space LLC
Original Assignee
Space Systems Loral LLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Assigned to SPACE SYSTEMS/LORAL, INC. reassignment SPACE SYSTEMS/LORAL, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KING, RONALD W., CAPPELLI, MARK ANTONY, GASCON, NICOLAS CLAUDE
Application filed by Space Systems Loral LLC filed Critical Space Systems Loral LLC
Priority to US13/223,041 priority Critical patent/US9145216B2/en
Assigned to SPACE SYSTEMS/LORAL, LLC, A DELAWARE LIMITED LIABILITY COMPANY reassignment SPACE SYSTEMS/LORAL, LLC, A DELAWARE LIMITED LIABILITY COMPANY CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SPACE SYSTEMS/LORAL, INC., A DELAWARE CORPORATION
Publication of US20130047578A1 publication Critical patent/US20130047578A1/en
Assigned to ROYAL BANK OF CANADA reassignment ROYAL BANK OF CANADA SECURITY AGREEMENT Assignors: SPACE SYSTEMS/LORAL, LLC
Publication of US9145216B2 publication Critical patent/US9145216B2/en
Application granted granted Critical
Assigned to ROYAL BANK OF CANADA, AS THE COLLATERAL AGENT reassignment ROYAL BANK OF CANADA, AS THE COLLATERAL AGENT SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DIGITALGLOBE, INC., MACDONALD, DETTWILER AND ASSOCIATES CORPORATION, MACDONALD, DETTWILER AND ASSOCIATES INC., MACDONALD, DETTWILER AND ASSOCIATES LTD., MDA GEOSPATIAL SERVICES INC., MDA INFORMATION SYSTEMS LLC, SPACE SYSTEMS/LORAL, LLC
Assigned to ROYAL BANK OF CANADA, AS COLLATERAL AGENT reassignment ROYAL BANK OF CANADA, AS COLLATERAL AGENT AMENDED AND RESTATED U.S. PATENT AND TRADEMARK SECURITY AGREEMENT Assignors: SPACE SYSTEMS/LORAL, LLC
Assigned to WILMINGTON TRUST, NATIONAL ASSOCIATION, - AS NOTES COLLATERAL AGENT reassignment WILMINGTON TRUST, NATIONAL ASSOCIATION, - AS NOTES COLLATERAL AGENT SECURITY AGREEMENT (NOTES) Assignors: DIGITALGLOBE, INC., RADIANT GEOSPATIAL SOLUTIONS LLC, SPACE SYSTEMS/LORAL, LLC (F/K/A SPACE SYSTEMS/LORAL INC.)
Assigned to WILMINGTON TRUST, NATIONAL ASSOCIATION, AS NOTES COLLATERAL AGENT reassignment WILMINGTON TRUST, NATIONAL ASSOCIATION, AS NOTES COLLATERAL AGENT PATENT SECURITY AGREEMENT Assignors: SPACE SYSTEMS/LORAL, LLC
Assigned to ROYAL BANK OF CANADA reassignment ROYAL BANK OF CANADA SECURITY AGREEMENT Assignors: Maxar Intelligence Inc., MAXAR SPACE LLC
Assigned to WILMINGTON TRUST, NATIONAL ASSOCIATION reassignment WILMINGTON TRUST, NATIONAL ASSOCIATION SECURITY AGREEMENT Assignors: Maxar Intelligence Inc., MAXAR SPACE LLC
Assigned to DIGITALGLOBE, INC., RADIANT GEOSPATIAL SOLUTIONS LLC, SPACE SYSTEMS/LORAL, LLC reassignment DIGITALGLOBE, INC. RELEASE BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: WILMINGTON TRUST, NATIONAL ASSOCIATION
Assigned to MAXAR SPACE LLC, Maxar Intelligence Inc. reassignment MAXAR SPACE LLC TERMINATION AND RELEASE OF SECURITY INTEREST IN PATENTS AND TRADEMARKS - RELEASE OF REEL/FRAME 051258/0720 Assignors: ROYAL BANK OF CANADA, AS AGENT
Assigned to MAXAR SPACE LLC, Maxar Intelligence Inc. reassignment MAXAR SPACE LLC TERMINATION AND RELEASE OF SECURITY INTEREST IN PATENTS AND TRADEMARKS - RELEASE OF REEL/FRAME 044167/0396 Assignors: ROYAL BANK OF CANADA, AS AGENT
Assigned to MAXAR SPACE LLC, Maxar Intelligence Inc. reassignment MAXAR SPACE LLC TERMINATION AND RELEASE OF PATENT SECURITY AGREEMENT - RELEASE OF REEL/FRAME 060389/0782 Assignors: WILMINGTON TRUST, NATIONAL ASSOCIATION, AS COLLATERAL AGENT
Assigned to SIXTH STREET LENDING PARTNERS, AS ADMINISTRATIVE AGENT reassignment SIXTH STREET LENDING PARTNERS, AS ADMINISTRATIVE AGENT INTELLECTUAL PROPERTY SECURITY AGREEMENT Assignors: Aurora Insight Inc., MAXAR INTELLIGENCE INC. (F/K/A DIGITALGLOBE, INC.), MAXAR MISSION SOLUTIONS INC. ((F/K/A RADIANT MISSION SOLUTIONS INC. (F/K/A THE RADIANT GROUP, INC.)), MAXAR SPACE LLC (F/K/A SPACE SYSTEMS/LORAL, LLC), MAXAR SPACE ROBOTICS LLC ((F/K/A SSL ROBOTICS LLC) (F/K/A MDA US SYSTEMS LLC)), MAXAR TECHNOLOGIES HOLDINGS INC., SPATIAL ENERGY, LLC
Assigned to MAXAR SPACE LLC, Maxar Intelligence Inc. reassignment MAXAR SPACE LLC RELEASE (REEL 060389/FRAME 0720) Assignors: ROYAL BANK OF CANADA
Assigned to MAXAR SPACE LLC reassignment MAXAR SPACE LLC CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SPACE SYSTEMS/LORAL, LLC
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40Arrangements or adaptations of propulsion systems
    • B64G1/402Propellant tanks; Feeding propellants
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40Arrangements or adaptations of propulsion systems
    • B64G1/403Solid propellant rocket engines
    • B64G1/404Hybrid rocket engines
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/72Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/94Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • F03H1/0006Details applicable to different types of plasma thrusters
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • F03H1/0006Details applicable to different types of plasma thrusters
    • F03H1/0012Means for supplying the propellant
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • F03H1/0037Electrostatic ion thrusters
    • F03H1/0043Electrostatic ion thrusters characterised by the acceleration grid
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • F03H1/0037Electrostatic ion thrusters
    • F03H1/005Electrostatic ion thrusters using field emission, e.g. Field Emission Electric Propulsion [FEEP]
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • F03H1/0037Electrostatic ion thrusters
    • F03H1/0062Electrostatic ion thrusters grid-less with an applied magnetic field
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • F03H1/0037Electrostatic ion thrusters
    • F03H1/0062Electrostatic ion thrusters grid-less with an applied magnetic field
    • F03H1/0068Electrostatic ion thrusters grid-less with an applied magnetic field with a central channel, e.g. end-Hall type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • F03H1/0037Electrostatic ion thrusters
    • F03H1/0062Electrostatic ion thrusters grid-less with an applied magnetic field
    • F03H1/0075Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift

Definitions

  • This invention relates generally to a spacecraft propulsion system, and particularly to a unified chemical electric propulsion system having a single propellant used by both a chemical thruster and an electrostatic or electromagnetic thruster.
  • Spacecraft propulsion systems generally include thrusters, which may be broadly categorized as either “chemical” or “electric” based on the respective primary energy source.
  • Chemical thrusters whether the propellant is solid or liquid, monopropellant or bipropellant, deliver thrust by converting chemical energy stored in the propellant to kinetic energy delivered to combustion products of the chemical propellant.
  • Chemical thrusters as the term is used herein, and in the claims, also include electrothermal thrusters such as arcjets, described for example in U.S. Pat. Nos. 5,485,721 and 5,819,526, that are configured to use electrical energy to increase the temperature, and, therefore, the velocity of the combustion products of chemical propellants.
  • an electric thruster converts electrical energy to propellant kinetic energy substantially without regard to any chemical energy the propellant may possess.
  • an electric thruster may operate by ionizing and accelerating a gaseous propellant, where the propellant is a noble gas of a heavy element, such as xenon or argon. Irrespective of the selected propellant, a negligible amount of thrust results from energy chemically stored in the propellant.
  • electric thruster as used herein and in the claims, encompasses an electrostatic thruster, an electromagnetic thruster, a Hall effect thruster, a wakefield accelerator, and a traveling wave accelerator, for example.
  • Chemical thrusters suitable for spacecraft propulsion systems may deliver relatively high thrust of 10-1000 newtons, for example, substantially irrespective of spacecraft power limitations, but such thrusters are generally incapable of operating at a specific impulse (I sp ) higher than 500 seconds.
  • Electric thrusters may operate at an I sp of 1000-4000 seconds, but spacecraft power constraints, at least, practically constrain thrust levels to well less than one newton.
  • each thruster assigned to a propulsion subsystem having its own dedicated propellants and its own dedicated propellant supply arrangements.
  • a unified spacecraft propulsion system having one or more chemical thrusters and one or more electric thrusters may, advantageously, operate with a single, common, propellant.
  • the system offers a wide range of thrust and I sp , while avoiding the overhead penalty of requiring separate, dedicated propellants and propellant supply arrangements for each of two types of propellants.
  • a spacecraft propulsion system includes at least one chemical thruster, having a gas generator and a high thrust accelerator and at least one electric thruster, having a plasma generator and a high specific impulse (Isp) accelerator.
  • the spacecraft propulsion system includes a propellant supply arrangement that stores a propellant; and at least one propellant conditioning arrangement, disposed between the propellant supply arrangement and the at least one plasma generator.
  • the propellant condition arrangement is configured to receive propellant from the propellant supply arrangement and convert the received propellant into one or more selected chemical species in a thermodynamic phase, the selected chemical species in the thermodynamic phase being readily ionizable.
  • the propellant supply arrangement is configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement; and a first flow path connects the propellant supply arrangement with the gas generator, and a second flow path connects the propellant supply arrangement with the plasma generator.
  • the propellant may be of a type selected from the group consisting of solid, liquid monopropellant, liquid bipropellant.
  • the propellant is selected from the group consisting of hydroxylammonium nitrate (H 4 N 2 O 4 ), hydrogen peroxide, ammonium dinitramide (H 4 N 4 O 4 ), nitrous oxide, and water.
  • the chemical thruster may operable to deliver at least one newton of thrust
  • the electric thruster may be configured to deliver a specific impulse of at least 500 seconds and be of a type selected from the group consisting of: a Hall accelerator, a gridded electrostatic accelerator, a cross field (E ⁇ B) accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a wakefield accelerator, a traveling wave accelerator, and an ion cyclotron resonance heater combined with a magnetic nozzle.
  • the gas generator may be of a type selected from the group consisting of: a catalytic device, an electric heater, and a combustion chamber.
  • the propellant supply arrangement may be configured to direct the propellant through a selectable one of the first flow path and the second flow path.
  • system may also include a power conditioning arrangement that tailors an input power from a spacecraft electric power supply to the requirements of the chemical thruster and the electric thruster.
  • a propulsion system includes at least one chemical thruster, at least one electric thruster, of a type selected from the group consisting of: a Hall accelerator, a gridded electrostatic accelerator, a cross field (E ⁇ B) accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a wakefield accelerator, a traveling wave accelerator, and an ion cyclotron resonance heater combined with a magnetic nozzle; and a propellant supply arrangement that stores a propellant.
  • the propellant is commonly supplied from the propellant supply arrangement to each of the chemical thruster and the electric thruster.
  • the chemical thruster may include a gas generator and a high thrust accelerator; the electric thruster, may include a plasma generator and a high specific impulse (Isp) accelerator.
  • a propellant conditioning arrangement may be disposed between the propellant supply arrangement and the plasma generator, configured to receive propellant from the propellant supply arrangement and convert the received propellant into one or more selected chemical species in a thermodynamic phase, the selected chemical species in the thermodynamic phase being readily ionizable.
  • the propellant supply arrangement may be configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement; and a first flow path may connects propellant supply arrangement with the gas generator, and a second flow path may connect propellant supply arrangement with the plasma generator.
  • FIG. 1 illustrates an example of chemical and electric propulsion subsystems of the prior art.
  • FIG. 2 illustrates a block diagram of an embodiment of a unified chemical electric propulsion system.
  • spacecraft spacecraft
  • spacecraft spacecraft
  • satellite spacecraft
  • vehicle vehicle
  • a unified spacecraft propulsion system having one or more chemical thrusters and one or more electric thrusters may, advantageously, operate with a single, common, propellant.
  • the system offers a wide range of thrust and I sp , while avoiding a need for a separate, dedicated propellant supply arrangements for each of two types of propellants.
  • more challenging satellite mission objectives may be enabled by the unified propulsion system, including, for example, multiple rapid repositioning of telecommunication satellites in geosynchronous orbit, large altitude and inclination changes for observation satellites in low earth orbit, debris avoidance, evasive maneuvers, formation flying to enable fractionated space vehicles, as well as more efficient interplanetary missions.
  • a propulsion system 200 may include a common propellant supply arrangement 205 that may be configured to operate with either or both of a chemical thruster 230 and an electric thruster 240 . It will be understood that, although only one each chemical thruster 230 and electric thruster 240 are illustrated for sake of clarity, a spacecraft propulsion system may have more than one of each type of device.
  • Propellant supply arrangement 205 may include one or more propellant tanks, or plenums, wherein a propellant is stored, and an arrangement of valves, regulators, filters and other propellant management and servicing devices.
  • the propellant may be a liquid propellant, and propellant supply arrangement 205 may also include devices for storing and/or regulating a pressurant, such as helium, for example.
  • the propellant may be a monopropellant such as hydrazine, for example.
  • the propellant is a bipropellant
  • propellant storage arrangement 205 may include at least two plenums, and provide separate storage for each of a fuel and an oxidizer.
  • the propellant may be a solid propellant.
  • the propellant may be a low-toxicity, “green” propellant, such as HAN (hydroxylammonium nitrate, H 4 N 2 O 4 ), hydrogen peroxide, ADN (ammonium dinitramide, H 4 N 4 O 4 ), nitrous oxide or water, for example.
  • HAN hydroxylammonium nitrate, H 4 N 2 O 4
  • ADN ammonium dinitramide, H 4 N 4 O 4
  • nitrous oxide or water for example.
  • Propellant supply arrangement 205 may be configured to provide for control and monitoring of propellant flow rates and pressures, and provide, for example, service means for propellant loading and propulsion system testing. Moreover, propellant supply arrangement 205 may provide for selection and isolation of one or more chemical or electric thrusters. Advantageously, propellant supply arrangement 205 is configured to selectably control propellant flow rate, depending on thrust level desired, and type of thruster to be operated. For example, when the type of thruster to be operated is electric thruster 240 , an appropriate propellant flow rate may be an order of magnitude or more lower than a propellant flow rate appropriate for operation of chemical thruster 230 .
  • Propellant conditioning arrangement 215 may be configured to convert the common propellant into chemical species in a thermodynamic phase that can be readily ionized to generate a plasma in an electric thruster.
  • a gas filtering element (not shown) may be disposed between propellant conditioning arrangement 215 and plasma generator 242 .
  • the gas filtering element may, for example, be configured to filter chemical species output from propellant conditioning arrangement 215 , so that only selected species reach plasma generator 242 .
  • molecular and/or atomic species that are most appropriate for dissociation and ionization, and/or plasma acceleration may be selected.
  • Power conditioning arrangement 225 may be configured to tailor an input power from the spacecraft electric power supply 10 to the requirements of the propulsion system.
  • input power from the spacecraft electric power supply may be provided at a single regulated or unregulated DC voltage.
  • Electric thruster 240 and propellant conditioning arrangement 215 may require AC and/or DC power inputs having a variety of regulation, voltage and current requirements.
  • power conditioning arrangement 225 may be configured to provide an appropriately tailored output to electric thruster 240 propellant conditioning arrangement 215 .
  • valving associated with chemical thruster 230 and other components of propulsion system 200 may require various low-voltage power inputs, and, in an embodiment, power conditioning arrangement 225 may also be configured to provide an appropriate output to such components.
  • chemical thruster 230 may consist of gas generator 232 and high thrust accelerator 234 .
  • Gas generator 232 may include, for example, a catalytic device for decomposing a monopropellant, an electric heater, and/or a combustion chamber wherein a fuel and oxidizer are combusted.
  • High thrust accelerator 234 in an embodiment, may be a nozzle configured to receive and expand the combustion products from gas generator 232 to produce thrust. It will be understood that gas generator 232 and high thrust accelerator 234 may be elements of an integrated device, or separately arranged.
  • electric thruster 240 may consist of plasma generator 242 and a high Isp accelerator 244 . It will be understood that plasma generator 242 and accelerator 244 may be elements of an integrated device, or separately arranged. Electric thruster 240 may be configured, for example, as a closed drift, electron accelerator (Hall accelerator), a gridded electrostatic accelerator, a cross field (E ⁇ B) accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a wakefield accelerator, a traveling wave accelerator, or an ion cyclotron resonance heater combined with a magnetic nozzle.
  • Hal accelerator electron accelerator
  • E ⁇ B cross field
  • pulsed plasma thruster a pulsed inductive thruster
  • field-reversed configuration plasma thruster a wakefield accelerator
  • traveling wave accelerator or an ion cyclotron resonance heater combined with a magnetic nozzle.
  • Plasma generator 242 may include, for example, an arrangement configured to ionize chemical species received from propellant conditioning arrangement 215 .
  • the chemical species are anticipated to include, for example, hydrogen, oxygen, nitrogen, carbon, and water, having an atomic mass and ionization efficiency indicated in Table I.
  • plasma generator 242 may be configured to effect molecular species dissociation on the chemical species and to ionize atomic species.
  • Plasma may be produced, in an embodiment, by electron bombardment, resulting from an electrical discharge between a cathode and an anode.
  • a radio frequency (RF) or helicon discharge may be employed to generate a plasma.
  • plasma generator 242 may be configured to operate efficiently over a wide range of electric power settings and with multiple types of propellants by, for example, tuning a magnetic field and/or a power matching network.
  • Accelerator 244 may be configured to accelerate ionized plasma species produced by plasma generator 242 .
  • accelerator 244 may employ steady or unsteady electric and magnetic fields, generated by electrodes, magnets, and/or RF antennas to produce an electromagnetic field that accelerates ions produced by plasma generator 242 to a high exhaust velocity.
  • accelerator 244 may induce an ion exhaust velocity of 10,000 meters per second or greater.

Abstract

A spacecraft propulsion system has at least one chemical thruster, at least one electric thruster, a propellant supply arrangement that stores a propellant and a propellant conditioning arrangement configured to convert propellant into chemical species in a thermodynamic phase that can be readily ionized. The propellant is commonly supplied from the propellant storage device to each of the chemical thruster and the electric thruster. The chemical thruster has a gas generator and a high thrust accelerator; the electric thruster has a plasma generator and a high specific impulse accelerator. The propellant supply arrangement is configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement, and a first flow path connects propellant supply arrangement with the gas generator, and a second flow path connects propellant supply arrangement with the plasma generator.

Description

TECHNICAL FIELD
This invention relates generally to a spacecraft propulsion system, and particularly to a unified chemical electric propulsion system having a single propellant used by both a chemical thruster and an electrostatic or electromagnetic thruster.
BACKGROUND OF THE INVENTION
Spacecraft propulsion systems generally include thrusters, which may be broadly categorized as either “chemical” or “electric” based on the respective primary energy source.
Chemical thrusters, whether the propellant is solid or liquid, monopropellant or bipropellant, deliver thrust by converting chemical energy stored in the propellant to kinetic energy delivered to combustion products of the chemical propellant. Chemical thrusters, as the term is used herein, and in the claims, also include electrothermal thrusters such as arcjets, described for example in U.S. Pat. Nos. 5,485,721 and 5,819,526, that are configured to use electrical energy to increase the temperature, and, therefore, the velocity of the combustion products of chemical propellants.
In contrast, an electric thruster, as the term is used herein, and in the claims, converts electrical energy to propellant kinetic energy substantially without regard to any chemical energy the propellant may possess. For example, an electric thruster may operate by ionizing and accelerating a gaseous propellant, where the propellant is a noble gas of a heavy element, such as xenon or argon. Irrespective of the selected propellant, a negligible amount of thrust results from energy chemically stored in the propellant. The term electric thruster, as used herein and in the claims, encompasses an electrostatic thruster, an electromagnetic thruster, a Hall effect thruster, a wakefield accelerator, and a traveling wave accelerator, for example.
Chemical thrusters suitable for spacecraft propulsion systems may deliver relatively high thrust of 10-1000 newtons, for example, substantially irrespective of spacecraft power limitations, but such thrusters are generally incapable of operating at a specific impulse (Isp) higher than 500 seconds. Electric thrusters may operate at an Isp of 1000-4000 seconds, but spacecraft power constraints, at least, practically constrain thrust levels to well less than one newton.
During the course of a typical spacecraft mission there are times that a high thrust, low power thruster is desirable; at other times, however, a high Isp thruster is more advantageous. As a result, it is known, as illustrated in FIG. 1, to provide both chemical and electric thrusters on board a single spacecraft, each thruster assigned to a propulsion subsystem having its own dedicated propellants and its own dedicated propellant supply arrangements.
SUMMARY OF INVENTION
The present inventors have appreciated that a unified spacecraft propulsion system having one or more chemical thrusters and one or more electric thrusters may, advantageously, operate with a single, common, propellant.
Advantageously, the system offers a wide range of thrust and Isp, while avoiding the overhead penalty of requiring separate, dedicated propellants and propellant supply arrangements for each of two types of propellants.
In an embodiment, a spacecraft propulsion system includes at least one chemical thruster, having a gas generator and a high thrust accelerator and at least one electric thruster, having a plasma generator and a high specific impulse (Isp) accelerator. The spacecraft propulsion system includes a propellant supply arrangement that stores a propellant; and at least one propellant conditioning arrangement, disposed between the propellant supply arrangement and the at least one plasma generator. The propellant condition arrangement is configured to receive propellant from the propellant supply arrangement and convert the received propellant into one or more selected chemical species in a thermodynamic phase, the selected chemical species in the thermodynamic phase being readily ionizable. The propellant supply arrangement is configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement; and a first flow path connects the propellant supply arrangement with the gas generator, and a second flow path connects the propellant supply arrangement with the plasma generator.
In another embodiment the propellant may be of a type selected from the group consisting of solid, liquid monopropellant, liquid bipropellant.
In a further embodiment, the propellant is selected from the group consisting of hydroxylammonium nitrate (H4N2O4), hydrogen peroxide, ammonium dinitramide (H4N4O4), nitrous oxide, and water.
In another embodiment, the chemical thruster may operable to deliver at least one newton of thrust
In a yet further embodiment the electric thruster may be configured to deliver a specific impulse of at least 500 seconds and be of a type selected from the group consisting of: a Hall accelerator, a gridded electrostatic accelerator, a cross field (E×B) accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a wakefield accelerator, a traveling wave accelerator, and an ion cyclotron resonance heater combined with a magnetic nozzle.
In an embodiment, the gas generator may be of a type selected from the group consisting of: a catalytic device, an electric heater, and a combustion chamber.
In another embodiment, the propellant supply arrangement may be configured to direct the propellant through a selectable one of the first flow path and the second flow path.
In a further embodiment, the system may also include a power conditioning arrangement that tailors an input power from a spacecraft electric power supply to the requirements of the chemical thruster and the electric thruster.
In an embodiment, a propulsion system includes at least one chemical thruster, at least one electric thruster, of a type selected from the group consisting of: a Hall accelerator, a gridded electrostatic accelerator, a cross field (E×B) accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a wakefield accelerator, a traveling wave accelerator, and an ion cyclotron resonance heater combined with a magnetic nozzle; and a propellant supply arrangement that stores a propellant. The propellant is commonly supplied from the propellant supply arrangement to each of the chemical thruster and the electric thruster.
In an embodiment, the chemical thruster may include a gas generator and a high thrust accelerator; the electric thruster, may include a plasma generator and a high specific impulse (Isp) accelerator. A propellant conditioning arrangement may be disposed between the propellant supply arrangement and the plasma generator, configured to receive propellant from the propellant supply arrangement and convert the received propellant into one or more selected chemical species in a thermodynamic phase, the selected chemical species in the thermodynamic phase being readily ionizable. The propellant supply arrangement may be configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement; and a first flow path may connects propellant supply arrangement with the gas generator, and a second flow path may connect propellant supply arrangement with the plasma generator.
BRIEF DESCRIPTION OF THE DRAWINGS
Features of the invention are more fully disclosed in the following detailed description of the preferred embodiments, reference being had to the accompanying drawings, in which:
FIG. 1 illustrates an example of chemical and electric propulsion subsystems of the prior art.
FIG. 2 illustrates a block diagram of an embodiment of a unified chemical electric propulsion system.
Throughout the drawings, the same reference numerals and characters, unless otherwise stated, are used to denote like features, elements, components, or portions of the illustrated embodiments. Moreover, while the subject invention will now be described in detail with reference to the drawings, the description is done in connection with the illustrative embodiments. It is intended that changes and modifications can be made to the described embodiments without departing from the true scope and spirit of the subject invention as defined by the appended claims.
DETAILED DESCRIPTION
Specific exemplary embodiments of the invention will now be described with reference to the accompanying drawings. This invention may, however, be embodied in many different forms, and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
It will be understood that when an element is referred to as being “connected” or “coupled” to another element, it can be directly connected or coupled to the other element, or intervening elements may be present. Furthermore, “connected” or “coupled” as used herein may include wirelessly connected or coupled. It will be understood that although the terms “first” and “second” are used herein to describe various elements, these elements should not be limited by these terms. These terms are used only to distinguish one element from another element. Thus, for example, a first user terminal could be termed a second user terminal, and similarly, a second user terminal may be termed a first user terminal without departing from the teachings of the present invention. As used herein, the term “and/or” includes any and all combinations of one or more of the associated listed items. The symbol “/” is also used as a shorthand notation for “and/or”.
The terms “spacecraft”, “satellite” and “vehicle” may be used interchangeably herein, and generally refer to any orbiting satellite, interplanetary vehicle, or spacecraft system.
The present inventors have appreciated that a unified spacecraft propulsion system having one or more chemical thrusters and one or more electric thrusters may, advantageously, operate with a single, common, propellant. Advantageously, the system offers a wide range of thrust and Isp, while avoiding a need for a separate, dedicated propellant supply arrangements for each of two types of propellants.
Other benefits of the techniques described hereinbelow include (1) increased payload to total vehicle mass ratio, (2) increased payload volume and mounting space, (3) reduction in manufacturing, testing and ground operation costs, (4) fewer mission and ground operation risks and failure mechanisms.
As a result of the above mentioned benefits, more challenging satellite mission objectives may be enabled by the unified propulsion system, including, for example, multiple rapid repositioning of telecommunication satellites in geosynchronous orbit, large altitude and inclination changes for observation satellites in low earth orbit, debris avoidance, evasive maneuvers, formation flying to enable fractionated space vehicles, as well as more efficient interplanetary missions.
In an embodiment, referring now to FIG. 2, a propulsion system 200 may include a common propellant supply arrangement 205 that may be configured to operate with either or both of a chemical thruster 230 and an electric thruster 240. It will be understood that, although only one each chemical thruster 230 and electric thruster 240 are illustrated for sake of clarity, a spacecraft propulsion system may have more than one of each type of device.
Propellant supply arrangement 205 may include one or more propellant tanks, or plenums, wherein a propellant is stored, and an arrangement of valves, regulators, filters and other propellant management and servicing devices. The propellant may be a liquid propellant, and propellant supply arrangement 205 may also include devices for storing and/or regulating a pressurant, such as helium, for example. The propellant may be a monopropellant such as hydrazine, for example. In an embodiment, the propellant is a bipropellant, and propellant storage arrangement 205 may include at least two plenums, and provide separate storage for each of a fuel and an oxidizer. In an embodiment, the propellant may be a solid propellant. Advantageously, the propellant may be a low-toxicity, “green” propellant, such as HAN (hydroxylammonium nitrate, H4N2O4), hydrogen peroxide, ADN (ammonium dinitramide, H4N4O4), nitrous oxide or water, for example.
Propellant supply arrangement 205 may be configured to provide for control and monitoring of propellant flow rates and pressures, and provide, for example, service means for propellant loading and propulsion system testing. Moreover, propellant supply arrangement 205 may provide for selection and isolation of one or more chemical or electric thrusters. Advantageously, propellant supply arrangement 205 is configured to selectably control propellant flow rate, depending on thrust level desired, and type of thruster to be operated. For example, when the type of thruster to be operated is electric thruster 240, an appropriate propellant flow rate may be an order of magnitude or more lower than a propellant flow rate appropriate for operation of chemical thruster 230.
Propellant conditioning arrangement 215 may be configured to convert the common propellant into chemical species in a thermodynamic phase that can be readily ionized to generate a plasma in an electric thruster. In an embodiment, a gas filtering element (not shown) may be disposed between propellant conditioning arrangement 215 and plasma generator 242. The gas filtering element may, for example, be configured to filter chemical species output from propellant conditioning arrangement 215, so that only selected species reach plasma generator 242. Advantageously, for example, molecular and/or atomic species that are most appropriate for dissociation and ionization, and/or plasma acceleration may be selected.
Power conditioning arrangement 225 may be configured to tailor an input power from the spacecraft electric power supply 10 to the requirements of the propulsion system. In an embodiment, for example, input power from the spacecraft electric power supply may be provided at a single regulated or unregulated DC voltage. Electric thruster 240 and propellant conditioning arrangement 215 may require AC and/or DC power inputs having a variety of regulation, voltage and current requirements. In an embodiment, power conditioning arrangement 225 may be configured to provide an appropriately tailored output to electric thruster 240 propellant conditioning arrangement 215. In an embodiment, valving associated with chemical thruster 230 and other components of propulsion system 200 may require various low-voltage power inputs, and, in an embodiment, power conditioning arrangement 225 may also be configured to provide an appropriate output to such components.
In an embodiment, chemical thruster 230 may consist of gas generator 232 and high thrust accelerator 234. Gas generator 232 may include, for example, a catalytic device for decomposing a monopropellant, an electric heater, and/or a combustion chamber wherein a fuel and oxidizer are combusted. High thrust accelerator 234, in an embodiment, may be a nozzle configured to receive and expand the combustion products from gas generator 232 to produce thrust. It will be understood that gas generator 232 and high thrust accelerator 234 may be elements of an integrated device, or separately arranged.
In an embodiment, electric thruster 240 may consist of plasma generator 242 and a high Isp accelerator 244. It will be understood that plasma generator 242 and accelerator 244 may be elements of an integrated device, or separately arranged. Electric thruster 240 may be configured, for example, as a closed drift, electron accelerator (Hall accelerator), a gridded electrostatic accelerator, a cross field (E×B) accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a wakefield accelerator, a traveling wave accelerator, or an ion cyclotron resonance heater combined with a magnetic nozzle.
Plasma generator 242 may include, for example, an arrangement configured to ionize chemical species received from propellant conditioning arrangement 215. The chemical species are anticipated to include, for example, hydrogen, oxygen, nitrogen, carbon, and water, having an atomic mass and ionization efficiency indicated in Table I. In an embodiment, plasma generator 242 may be configured to effect molecular species dissociation on the chemical species and to ionize atomic species. Plasma may be produced, in an embodiment, by electron bombardment, resulting from an electrical discharge between a cathode and an anode. In other embodiments, a radio frequency (RF) or helicon discharge may be employed to generate a plasma. Advantageously, plasma generator 242 may be configured to operate efficiently over a wide range of electric power settings and with multiple types of propellants by, for example, tuning a magnetic field and/or a power matching network.
TABLE I
Combustion Atomic Mass Ionization
Product (AMU) Efficiency (eV)
H2 2.016 13.6
O2 31.98 13.6
N2 28.02 14.5
H2O 18.01 32.2
C 12.01 11.3
Accelerator 244 may be configured to accelerate ionized plasma species produced by plasma generator 242. For example, accelerator 244 may employ steady or unsteady electric and magnetic fields, generated by electrodes, magnets, and/or RF antennas to produce an electromagnetic field that accelerates ions produced by plasma generator 242 to a high exhaust velocity. Advantageously, accelerator 244 may induce an ion exhaust velocity of 10,000 meters per second or greater.
Thus, a unified chemical electric propulsion system has been disclosed.
The foregoing merely illustrates principles of the invention. It will thus be appreciated that those skilled in the art will be able to devise numerous systems and methods which, although not explicitly shown or described herein, embody said principles of the invention and are thus within the spirit and scope of the invention as defined by the following claims.

Claims (13)

What is claimed is:
1. A spacecraft propulsion system comprising:
at least one chemical thruster, including a gas generator and a high thrust accelerator, the at least one chemical thruster configured to deliver at least 10 newtons of thrust;
at least one electric thruster, including a plasma generator and a high specific impulse (Isp) accelerator, the at least one electric thruster being of a type selected from the group consisting of: a Hall accelerator, a gridded electrostatic accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a wakefield accelerator, a traveling wave accelerator, and an ion cyclotron resonance heater combined with a magnetic nozzle;
a propellant supply arrangement that stores a propellant; and
at least one propellant conditioning arrangement, disposed between the propellant supply arrangement and the at least one electric thruster, and not between the propellant supply arrangement and the at least one chemical thruster, the propellant conditioning arrangement configured to receive propellant from the propellant supply arrangement and convert the received propellant into one or more selected chemical species in a thermodynamic phase;
wherein the propellant supply arrangement is configured to selectably control flow rate of the propellant from the propellant supply arrangement to a selectable one of the gas generator and the propellant conditioning arrangement, appropriate to a type of thruster selected to be operated and to provide for selection and isolation of the at least one chemical thruster and the at least one electric thruster; and
a first flow path connects the propellant supply arrangement with the gas generator, and a second flow path connects the propellant supply arrangement with the plasma generator.
2. The spacecraft propulsion system of claim 1, wherein the propellant is of a type selected from the group consisting of solid, liquid monopropellant, liquid bipropellant.
3. The spacecraft propulsion system of claim 1, wherein the propellant is selected from the group consisting of hydroxylammonium nitrate (H4N204), hydrogen peroxide, ammonium dinitramide (H4N404), nitrous oxide, and water.
4. The spacecraft propulsion system of claim 1, wherein the gas generator is of a type selected from the group consisting of: a catalytic device, an electric heater, and a combustion chamber.
5. The spacecraft propulsion system of claim 1, wherein the propellant supply arrangement is configured to direct the propellant through a selectable one of the first flow path and the second flow path.
6. The spacecraft propulsion system of claim 1, wherein the system further comprises a power conditioning arrangement that tailors an input power from a spacecraft electric power supply to the requirements of the at least one chemical thruster and the at least one electric thruster.
7. A propulsion system comprising:
at least one chemical thruster;
at least one electric thruster, of a type selected from the group consisting of: a Hall accelerator, a gridded electrostatic accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a wakefield accelerator, a traveling wave accelerator, and an ion cyclotron resonance heater combined with a magnetic nozzle;
a propellant supply arrangement that stores a propellant; and
a propellant conditioning arrangement disposed between the propellant supply arrangement and the at least one electric thruster, and not between the propellant supply arrangement and the at least one chemical thruster, the propellant conditioning arrangement configured to convert propellant into chemical species in a thermodynamic phase; wherein
the propellant is commonly supplied from the propellant supply arrangement to each of the at least one chemical thruster and the at least one electric thruster; and
the propellant supply arrangement is configured to selectably control flow rate of the propellant from the propellant supply arrangement to a selectable one of the at least one chemical thruster and the propellant conditioning arrangement, appropriate to a type of thruster selected to be operated and to provide for selection and isolation of the at least one chemical thruster and the at least one electric thruster.
8. The propulsion system of claim 7, wherein:
the at least one chemical thruster comprises a gas generator and a high thrust accelerator;
the at least one electric thruster, comprises a plasma generator and a high specific impulse (Isp) accelerator; and
a first flow path connects the propellant supply arrangement with the gas generator, and a second flow path connects the propellant supply arrangement with the plasma generator.
9. The propulsion system of claim 8, wherein the propellant is of a type selected from the group consisting of solid, liquid monopropellant, liquid bipropellant.
10. The propulsion system of claim 8, wherein the propellant is selected from the group consisting of hydroxylammonium nitrate (H4N204), hydrogen peroxide, ammonium dinitramide (H4N404), nitrous oxide, and water.
11. The propulsion system of claim 8, wherein the gas generator is of a type selected from the group consisting of: a catalytic device, an electric heater, and a combustion chamber.
12. The propulsion system of claim 8, wherein the propellant supply arrangement is configured to direct the propellant through a selectable one of the first flow path and the second flow path.
13. The propulsion system of claim 8, wherein the system further comprises a power conditioning arrangement that tailors an input power from a spacecraft electric power supply to the requirements of the at least one chemical thruster and the at least one electric thruster.
US13/223,041 2011-08-31 2011-08-31 Unified chemical electric propulsion system Active 2034-07-26 US9145216B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US13/223,041 US9145216B2 (en) 2011-08-31 2011-08-31 Unified chemical electric propulsion system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/223,041 US9145216B2 (en) 2011-08-31 2011-08-31 Unified chemical electric propulsion system

Publications (2)

Publication Number Publication Date
US20130047578A1 US20130047578A1 (en) 2013-02-28
US9145216B2 true US9145216B2 (en) 2015-09-29

Family

ID=47741649

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/223,041 Active 2034-07-26 US9145216B2 (en) 2011-08-31 2011-08-31 Unified chemical electric propulsion system

Country Status (1)

Country Link
US (1) US9145216B2 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107878783A (en) * 2017-10-12 2018-04-06 北京控制工程研究所 A kind of power supply propulsion system based on regeneratable fuel cell
EP3412582A1 (en) 2017-06-07 2018-12-12 Space Systems/Loral, LLC Cross-feeding propellant between stacked spacecraft
US10336475B1 (en) 2015-11-10 2019-07-02 Space Systems/Loral, Llc Flexible propulsion system
US11021273B1 (en) 2018-05-03 2021-06-01 Space Systems/Loral, Llc Unified spacecraft propellant management system for chemical and electric propulsion
US11346306B1 (en) 2019-01-03 2022-05-31 Ball Aerospace & Technologies Corp. Chemical and cold gas propellant systems and methods
US11498705B1 (en) 2019-05-09 2022-11-15 Ball Aerospace & Technology Corp. On orbit fluid propellant dispensing systems and methods
US20230136486A1 (en) * 2020-02-26 2023-05-04 The George Washington University Two-stage low-power and high-thrust to power electric propulsion system

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2986213B1 (en) * 2012-02-01 2014-10-10 Snecma SPIRAL PROPELLER WITH ELECTRICAL PROPULSION AND CHEMICAL WITH SOLID PROPERGOL
US20130327015A1 (en) * 2012-06-12 2013-12-12 Pamela Pollet Dual use hydrazine propulsion thruster system
GB201310632D0 (en) * 2013-06-14 2013-07-31 Prosser Richard An engine comprising a travelling wave magnetic field generator
JP6402020B2 (en) * 2014-12-15 2018-10-10 株式会社Ihiエアロスペース Propulsion device
WO2017023383A1 (en) * 2015-05-05 2017-02-09 Digital Solid State Propulsion, Inc. Liquid fueled pulsed plasma thruster
FR3065202B1 (en) * 2017-04-18 2020-07-17 Centre National D'etudes Spatiales SPACE PROPELLER
EP3620394A1 (en) * 2018-09-06 2020-03-11 Airbus Defence and Space Limited A propulsion system
US11554883B2 (en) * 2019-06-25 2023-01-17 Alexey Shashurin Liquid-fed pulsed plasma thruster for propelling nanosatellites
CN112613245B (en) * 2020-12-18 2024-03-12 中国人民解放军91550部队 Design method of laser pre-ionization induction plasma thruster

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4069664A (en) * 1974-01-24 1978-01-24 Hughes Aircraft Company Monopropellant thruster
US5170623A (en) * 1991-01-28 1992-12-15 Trw Inc. Hybrid chemical/electromagnetic propulsion system
US5651515A (en) * 1995-01-30 1997-07-29 Agence Spatiale Europeenne Method for re-orbiting a dual-mode propulsion geostationary spacecraft
US6438191B1 (en) * 1998-03-31 2002-08-20 Sandia Corporation Explosive scabbling of structural materials
US20040088910A1 (en) * 1998-04-15 2004-05-13 Van Den Berg Ronald Peter Monopropellant system
US20080121548A1 (en) * 2006-09-20 2008-05-29 The Boeing Company Coating for components requiring hydrogen peroxide compatibility
US20090029240A1 (en) * 2007-07-24 2009-01-29 A123 Systems, Inc. Battery cell design and methods of its construction
US20090148352A1 (en) * 2006-03-29 2009-06-11 Zubrin Robert M Portable gas generating device

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4069664A (en) * 1974-01-24 1978-01-24 Hughes Aircraft Company Monopropellant thruster
US5170623A (en) * 1991-01-28 1992-12-15 Trw Inc. Hybrid chemical/electromagnetic propulsion system
US5651515A (en) * 1995-01-30 1997-07-29 Agence Spatiale Europeenne Method for re-orbiting a dual-mode propulsion geostationary spacecraft
US6438191B1 (en) * 1998-03-31 2002-08-20 Sandia Corporation Explosive scabbling of structural materials
US20040088910A1 (en) * 1998-04-15 2004-05-13 Van Den Berg Ronald Peter Monopropellant system
US20090148352A1 (en) * 2006-03-29 2009-06-11 Zubrin Robert M Portable gas generating device
US20080121548A1 (en) * 2006-09-20 2008-05-29 The Boeing Company Coating for components requiring hydrogen peroxide compatibility
US20090029240A1 (en) * 2007-07-24 2009-01-29 A123 Systems, Inc. Battery cell design and methods of its construction

Non-Patent Citations (32)

* Cited by examiner, † Cited by third party
Title
Airbus Space Systems Hydrazine Thrusters-Heritage Models 10N thruster launched in 1977 http://cs.astrium.eads.net/sp/spacecraft-propulsion/hydrazine-thrusters/heritage-thrusters.html. *
Anflo, K., et al. (Jun. 2004) "Development Testing of 1-Newton ADN-Based Rocket Engines", Proceedings of the 2nd International Conference on Green Propellants for Space Propulsion ESA SP-557, Chia Laguna (Cagliara), Sardinia, Italy, Jun. 7-8, 2004, 4 pp.
Anflo, K., et al. (Mar. 2009) "Flight Demonstration of New Thruster and Green Propellant Technology on the PRISMA Satellite", Acta Astronautica 65 (2009) pp. 1238-1249 , 12 pp.
Astrium 1 Newton Thrusters http://cs.astrium.eads.net/sp/spacecraft-propulsion/hydrazine-thrusters/1n-thruster.html. *
Astrium EADS Hydrazine Thrusters Jan. 11, 2011 http://cs.astrium.eads.net/sp/spacecraft-propulsion/hydrazine-thrusters/index.html. *
Clark, The Magnetoplasmadynamic Arcjet, 1967, Pergammon Press, Astronautica Acta, vol. 13 pp. 315-325. *
Corey, Ronald L., et al. (Sep. 2009) "Electric Propulsion at Space Systems/Loral", IEPC-2009-270, The 31st International Electric Propulsion Conference, University of Michgan, Ann Arbor, Michigan, Sep. 20-24, 2009, 17 pp.
Dailey "The PIT MkV Pulsed Inductive Thruster" NASA 1993 http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19930023164.pdf. *
Feili, D., et al. (2009) "muNRIT-2.5-A New Optimized Microthruster of Giessen University", IEPC-2009-174, American Institute of Aeronautics and Astronautics, 9 pp.
Feili, D., et al. (2009) "μNRIT-2.5-A New Optimized Microthruster of Giessen University", IEPC-2009-174, American Institute of Aeronautics and Astronautics, 9 pp.
Frisbee, Robert H., et al. (Jul. 2005) "The Nuclear-Electric Pulsed Inductive Thruster (NuPIT): Mission Analysis for Prometheus", 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Tucson, Arizona, Jul. 10-13, 2005, 20 pp.
Gulczinski III, F.S. and Spores, R.A., "Analysis of Hall-effect Thrusters and Ion Engines for Orbit Transfer Missions," AIAA-96-2973, 32nd AIAA / ASME / SAE / ASEE Joint Propulsion Conference, Orlando, FL, Jul. 1996. *
Gulczinski, F., and Spores, R., "Analysis of Hall-effect thrusters and ion engines for orbit transfer missions," AIAA-96-2973, 32nd AIAA / ASME / SAE / ASEE Joint Propulsion Conference, Lake Buena Vista, FL, Jul. 1-3, 1996. *
Hong, I.S., et al. (Mar. 2000) "Ion-beam Characteristics of Novel Helicon Ion Sources for Different Plasma Parameters", Review of Scientific Instruments, vol. 1, No. 3, pp. 1385-1388, 4 pp.
Horisawa "Fundamental study on laser plasma accelerator for propulsion applications" 2002 Vacuum 65 (2002) 389-396 http://www.sciencedirect.com/science/article/pii/S0042207X0100447X. *
J.I.E. Jordan, Electric propulsion: which one for my spacecraft? Space Systems I course at JHU, Whiting School of Engineering, Dec. 6, 2000. http://www.stsci.edu/~jordan/other/electric-propulsion-3.pdf. *
J.I.E. Jordan, Electric propulsion: which one for my spacecraft? Space Systems I course at JHU, Whiting School of Engineering, Dec. 6, 2000. http://www.stsci.edu/˜jordan/other/electric-propulsion-3.pdf. *
Killinger, Rainer, et al. (2001) "Results of the 15000 Hours Lifetime Test for the RITA Ion Propulsion on ESA's ARTEMIS Satellite", IEPC-01-082, Astrium GmbH, Munchen, Germany, 10 pp.
Kirtley, David, et al. (2005) "Details on an Annular Field Reversed Configuration Plasma Device for Spacecraft Propulsion" IEPC-2005-171, University of Michigan, Ann Arbor, Michigan, 9 pp.
Kounalakis, M.E., et al. (1988) "Combustion of HAN-based Liquid Monopropellants Near the Thermodynamic Critical Point", Combustion and Flame, vol. 74, Issue 2, pp. 179-192, 14 pp.
Kuninaka, Hitoshi, et al. (Sep. 2007) "Re-ignition of Microwave Discharge Ion Engines on Hayabusa for Homeward Journey", IEPC-2007-9, The 30th International Electric Propulsion Conference, Florence, Italy, Sep. 17-20, 2007, 6 pp.
Lancellotti "Radiofrequency Plasma Thrusters: Modelling of Ion Cyclotron Resonance Heating and System Performance" 2007 AIAA http://www.esa.int/gsp/ACT/doc/PRO/ACT-RPR-PRO-JPC2007-TOPICA%20Vasimir%20 code%202007-5129.pdf. *
Miller S., Rovey J. Progress in modeling of pre-ionization and geometric effects on a field-reversed configu-ration plasma thruster, AIAA 2009-3733. http://enu.kz/repository/2009/AIAA-2009-3733.pdf. *
NASA Propulsion Systems http://history.nasa.gov/conghand/propulsn.htm Mar. 2010. *
Pavarin, D., et al. (Sep. 2009) "Design of 50 W Helicon Plasma Thruster" IEPC-2009-205, The 31st International Electric Propulsion Conference, University of Michigan, Sep. 20-24, 2009, 8 pp.
Saccoccia, G., et al. (Feb. 2000) "Electric Propulsion: A Key Technology for Space Missions in the New Millennium", Electric Propulsion Section, ESA Directorate for Technical and Operational Support, ESTEC, Noordwijk, The Netherlands, ESA Bulletin 101, Feb. 2000, 10 pp.
Slough, John, et al. (Sep. 2009) "Pulsed Plasmoid Propulsion: The ELF Thruster", IEPC-2009-265, The 31st International Electric Propulsion Conference, Ann Arbor, Michigan, Sep. 20-24, 2009, 24 pp.
Squire, J.P., et al. (2000) "Helicon Plasma Injector and Ion Cyclotron Acceleration Development in the VASIMR Experiment", AIAA-2000-3752, 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Huntsville, Alabama, Jul. 17-19, 2000, 8 pp.
Squire, Jared P., et al. (Sep. 2009) "Superconducting 200 kW VASIMR Experiment and Integrated Testing", IEPC-2009-209, The 31st International Electric Propulsion Conference, University of Michigan, Ann Arbor, Michigan, Sep. 20-24, 2009, 8 pp.
Tahara, Hirokazu (Jul. 2003) "An Overview of Electric Propulsion Activities in Japan", The 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit Jul. 20-23, 2003, Huntsville, Alabama, 25 pp.
Tillerson, Michael, et al. (2003) "Distributed Coordination and Control of Formation Flying Spacecraft" MIT Department of Aeronautics and Astronautics, 6 pp.
Toki, Kyoichiro, et al. (2009) "Plasma Acceleration in a Compact Helicon Source Using RF Antennae", The Japan Society of Plasma Science and Nuclear Fusion Research Series, vol. 8, 2009, pp. 25-30, 6 pp.

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10336475B1 (en) 2015-11-10 2019-07-02 Space Systems/Loral, Llc Flexible propulsion system
EP3412582A1 (en) 2017-06-07 2018-12-12 Space Systems/Loral, LLC Cross-feeding propellant between stacked spacecraft
US10589879B2 (en) 2017-06-07 2020-03-17 Space Systems/Loral, Llc Cross-feeding propellant between stacked spacecraft
CN107878783A (en) * 2017-10-12 2018-04-06 北京控制工程研究所 A kind of power supply propulsion system based on regeneratable fuel cell
CN107878783B (en) * 2017-10-12 2020-04-10 北京控制工程研究所 Power propulsion system based on renewable fuel cell
US11021273B1 (en) 2018-05-03 2021-06-01 Space Systems/Loral, Llc Unified spacecraft propellant management system for chemical and electric propulsion
US11346306B1 (en) 2019-01-03 2022-05-31 Ball Aerospace & Technologies Corp. Chemical and cold gas propellant systems and methods
US11498705B1 (en) 2019-05-09 2022-11-15 Ball Aerospace & Technology Corp. On orbit fluid propellant dispensing systems and methods
US20230136486A1 (en) * 2020-02-26 2023-05-04 The George Washington University Two-stage low-power and high-thrust to power electric propulsion system

Also Published As

Publication number Publication date
US20130047578A1 (en) 2013-02-28

Similar Documents

Publication Publication Date Title
US9145216B2 (en) Unified chemical electric propulsion system
US11365016B2 (en) Electrodeless plasma thruster
US7395656B2 (en) Dual mode hybrid electric thruster
US6640535B2 (en) Linear gridless ion thruster
Koizumi et al. Miniature microwave discharge ion thruster driven by 1 watt microwave power
US11325727B2 (en) Converging/diverging magnetic nozzle
WO2010036291A2 (en) Ionic liquid multi-mode propulsion system
US11021273B1 (en) Unified spacecraft propellant management system for chemical and electric propulsion
Schwertheim et al. The water electrolysis hall effect thruster (wet-het): Paving the way to dual mode chemical-electric water propulsion
US20210309396A1 (en) A propulsion system
US20210309395A1 (en) A propulsion system
Spence et al. Electrospray propulsion systems for small satellites
Koizumi et al. Performance evaluation of a miniature ion thruster μ1 with a unipolar and bipolar operation
Sheth Spacecraft Electric Propulsion–A review
Tsay et al. Flight development of iodine BIT-3 RF ion propulsion system for SLS EM-1 CubeSats
Peterson et al. Performance and plume characterization of a helicon Hall thruster
Mani et al. Electric propulsion characterization for a stand-alone Mars CubeSat
Leiter et al. Six decades of thrust-the Ariane Group radiofrequency ion thrusters and systems family
Dropmann et al. Low Power Arcjet Application for End of Life Satellite Servicing
Leiter et al. The Ariane group electric propulsion program 2019–2020
Jones Results of large vacuum facility tests of an MPD arc thruster.
Nakagawa et al. Miniature Water Ion Thruster; 1 km/s-class Delta-V for a 6U CubeSat
Porst et al. EP GEO Propulsion Platform
Lee et al. Annular Hall thruster with high anode efficiency
Loeb Electric propulsion technology status and development plans-European programs

Legal Events

Date Code Title Description
AS Assignment

Owner name: SPACE SYSTEMS/LORAL, INC., CALIFORNIA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GASCON, NICOLAS CLAUDE;CAPPELLI, MARK ANTONY;KING, RONALD W.;SIGNING DATES FROM 20110808 TO 20110829;REEL/FRAME:026841/0030

AS Assignment

Owner name: SPACE SYSTEMS/LORAL, LLC, A DELAWARE LIMITED LIABI

Free format text: CHANGE OF NAME;ASSIGNOR:SPACE SYSTEMS/LORAL, INC., A DELAWARE CORPORATION;REEL/FRAME:029340/0409

Effective date: 20121102

AS Assignment

Owner name: ROYAL BANK OF CANADA, CANADA

Free format text: SECURITY AGREEMENT;ASSIGNOR:SPACE SYSTEMS/LORAL, LLC;REEL/FRAME:030312/0078

Effective date: 20121102

STCF Information on status: patent grant

Free format text: PATENTED CASE

AS Assignment

Owner name: ROYAL BANK OF CANADA, AS THE COLLATERAL AGENT, CANADA

Free format text: SECURITY INTEREST;ASSIGNORS:DIGITALGLOBE, INC.;MACDONALD, DETTWILER AND ASSOCIATES LTD.;MACDONALD, DETTWILER AND ASSOCIATES CORPORATION;AND OTHERS;REEL/FRAME:044167/0396

Effective date: 20171005

Owner name: ROYAL BANK OF CANADA, AS THE COLLATERAL AGENT, CAN

Free format text: SECURITY INTEREST;ASSIGNORS:DIGITALGLOBE, INC.;MACDONALD, DETTWILER AND ASSOCIATES LTD.;MACDONALD, DETTWILER AND ASSOCIATES CORPORATION;AND OTHERS;REEL/FRAME:044167/0396

Effective date: 20171005

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 4

AS Assignment

Owner name: ROYAL BANK OF CANADA, AS COLLATERAL AGENT, CANADA

Free format text: AMENDED AND RESTATED U.S. PATENT AND TRADEMARK SECURITY AGREEMENT;ASSIGNOR:SPACE SYSTEMS/LORAL, LLC;REEL/FRAME:051258/0720

Effective date: 20191211

AS Assignment

Owner name: WILMINGTON TRUST, NATIONAL ASSOCIATION, - AS NOTES

Free format text: SECURITY AGREEMENT (NOTES);ASSIGNORS:DIGITALGLOBE, INC.;RADIANT GEOSPATIAL SOLUTIONS LLC;SPACE SYSTEMS/LORAL, LLC (F/K/A SPACE SYSTEMS/LORAL INC.);REEL/FRAME:051262/0824

Effective date: 20191211

Owner name: WILMINGTON TRUST, NATIONAL ASSOCIATION, - AS NOTES COLLATERAL AGENT, TEXAS

Free format text: SECURITY AGREEMENT (NOTES);ASSIGNORS:DIGITALGLOBE, INC.;RADIANT GEOSPATIAL SOLUTIONS LLC;SPACE SYSTEMS/LORAL, LLC (F/K/A SPACE SYSTEMS/LORAL INC.);REEL/FRAME:051262/0824

Effective date: 20191211

AS Assignment

Owner name: WILMINGTON TRUST, NATIONAL ASSOCIATION, AS NOTES COLLATERAL AGENT, CONNECTICUT

Free format text: PATENT SECURITY AGREEMENT;ASSIGNOR:SPACE SYSTEMS/LORAL, LLC;REEL/FRAME:053866/0810

Effective date: 20200922

AS Assignment

Owner name: ROYAL BANK OF CANADA, CANADA

Free format text: SECURITY AGREEMENT;ASSIGNORS:MAXAR INTELLIGENCE INC.;MAXAR SPACE LLC;REEL/FRAME:060389/0720

Effective date: 20220614

AS Assignment

Owner name: WILMINGTON TRUST, NATIONAL ASSOCIATION, TEXAS

Free format text: SECURITY AGREEMENT;ASSIGNORS:MAXAR INTELLIGENCE INC.;MAXAR SPACE LLC;REEL/FRAME:060389/0782

Effective date: 20220614

AS Assignment

Owner name: RADIANT GEOSPATIAL SOLUTIONS LLC, COLORADO

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:WILMINGTON TRUST, NATIONAL ASSOCIATION;REEL/FRAME:060390/0282

Effective date: 20220614

Owner name: SPACE SYSTEMS/LORAL, LLC, CALIFORNIA

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:WILMINGTON TRUST, NATIONAL ASSOCIATION;REEL/FRAME:060390/0282

Effective date: 20220614

Owner name: DIGITALGLOBE, INC., COLORADO

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:WILMINGTON TRUST, NATIONAL ASSOCIATION;REEL/FRAME:060390/0282

Effective date: 20220614

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1552); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 8

AS Assignment

Owner name: MAXAR SPACE LLC, CALIFORNIA

Free format text: TERMINATION AND RELEASE OF SECURITY INTEREST IN PATENTS AND TRADEMARKS - RELEASE OF REEL/FRAME 044167/0396;ASSIGNOR:ROYAL BANK OF CANADA, AS AGENT;REEL/FRAME:063543/0001

Effective date: 20230503

Owner name: MAXAR INTELLIGENCE INC., COLORADO

Free format text: TERMINATION AND RELEASE OF SECURITY INTEREST IN PATENTS AND TRADEMARKS - RELEASE OF REEL/FRAME 044167/0396;ASSIGNOR:ROYAL BANK OF CANADA, AS AGENT;REEL/FRAME:063543/0001

Effective date: 20230503

Owner name: MAXAR SPACE LLC, CALIFORNIA

Free format text: TERMINATION AND RELEASE OF PATENT SECURITY AGREEMENT - RELEASE OF REEL/FRAME 060389/0782;ASSIGNOR:WILMINGTON TRUST, NATIONAL ASSOCIATION, AS COLLATERAL AGENT;REEL/FRAME:063544/0074

Effective date: 20230503

Owner name: MAXAR INTELLIGENCE INC., COLORADO

Free format text: TERMINATION AND RELEASE OF PATENT SECURITY AGREEMENT - RELEASE OF REEL/FRAME 060389/0782;ASSIGNOR:WILMINGTON TRUST, NATIONAL ASSOCIATION, AS COLLATERAL AGENT;REEL/FRAME:063544/0074

Effective date: 20230503

Owner name: MAXAR SPACE LLC, CALIFORNIA

Free format text: TERMINATION AND RELEASE OF SECURITY INTEREST IN PATENTS AND TRADEMARKS - RELEASE OF REEL/FRAME 051258/0720;ASSIGNOR:ROYAL BANK OF CANADA, AS AGENT;REEL/FRAME:063542/0543

Effective date: 20230503

Owner name: MAXAR INTELLIGENCE INC., COLORADO

Free format text: TERMINATION AND RELEASE OF SECURITY INTEREST IN PATENTS AND TRADEMARKS - RELEASE OF REEL/FRAME 051258/0720;ASSIGNOR:ROYAL BANK OF CANADA, AS AGENT;REEL/FRAME:063542/0543

Effective date: 20230503

AS Assignment

Owner name: SIXTH STREET LENDING PARTNERS, AS ADMINISTRATIVE AGENT, TEXAS

Free format text: INTELLECTUAL PROPERTY SECURITY AGREEMENT;ASSIGNORS:MAXAR INTELLIGENCE INC. (F/K/A DIGITALGLOBE, INC.);AURORA INSIGHT INC.;MAXAR MISSION SOLUTIONS INC. ((F/K/A RADIANT MISSION SOLUTIONS INC. (F/K/A THE RADIANT GROUP, INC.));AND OTHERS;REEL/FRAME:063660/0138

Effective date: 20230503

AS Assignment

Owner name: MAXAR INTELLIGENCE INC., COLORADO

Free format text: RELEASE (REEL 060389/FRAME 0720);ASSIGNOR:ROYAL BANK OF CANADA;REEL/FRAME:063633/0431

Effective date: 20230503

Owner name: MAXAR SPACE LLC, CALIFORNIA

Free format text: RELEASE (REEL 060389/FRAME 0720);ASSIGNOR:ROYAL BANK OF CANADA;REEL/FRAME:063633/0431

Effective date: 20230503

AS Assignment

Owner name: MAXAR SPACE LLC, CALIFORNIA

Free format text: CHANGE OF NAME;ASSIGNOR:SPACE SYSTEMS/LORAL, LLC;REEL/FRAME:063861/0016

Effective date: 20210101